CA2321640A1 - Compressor endwall bleed system - Google Patents

Compressor endwall bleed system Download PDF

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Publication number
CA2321640A1
CA2321640A1 CA002321640A CA2321640A CA2321640A1 CA 2321640 A1 CA2321640 A1 CA 2321640A1 CA 002321640 A CA002321640 A CA 002321640A CA 2321640 A CA2321640 A CA 2321640A CA 2321640 A1 CA2321640 A1 CA 2321640A1
Authority
CA
Canada
Prior art keywords
bleed
endwall
bleed system
shrouded rotor
slots
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CA002321640A
Other languages
French (fr)
Other versions
CA2321640C (en
Inventor
Robert A. Ress, Jr.
Jeffrey L. Hansen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce North American Technologies Inc
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of CA2321640A1 publication Critical patent/CA2321640A1/en
Application granted granted Critical
Publication of CA2321640C publication Critical patent/CA2321640C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Feed For Specific Animals (AREA)

Abstract

A compression system endwall bleed system having a plurality of bleed slots formed in a mechanical housing downstream of a rotating shrouded rotor. In one embodiment, the plurality of bleed slots bleed off a separated tip boundary layer to relieve back pressure associated with this blockage. A sealing structure downstream of the shrouded rotor is utilized to minimize working fluid leakage ahead of the plurality of bleed slots.
CA002321640A 1998-02-26 1999-02-26 Compressor endwall bleed system Expired - Fee Related CA2321640C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US7602698P 1998-02-26 1998-02-26
US60/076,026 1998-02-26
PCT/US1999/004319 WO1999051866A2 (en) 1998-02-26 1999-02-26 Compressor endwall bleed system

Publications (2)

Publication Number Publication Date
CA2321640A1 true CA2321640A1 (en) 1999-10-14
CA2321640C CA2321640C (en) 2004-01-06

Family

ID=22129473

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002321640A Expired - Fee Related CA2321640C (en) 1998-02-26 1999-02-26 Compressor endwall bleed system

Country Status (8)

Country Link
US (1) US6428271B1 (en)
EP (1) EP1147291B1 (en)
JP (1) JP2003517525A (en)
AT (1) ATE371097T1 (en)
AU (1) AU5201699A (en)
CA (1) CA2321640C (en)
DE (1) DE69936939T2 (en)
WO (1) WO1999051866A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades

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JP4893110B2 (en) * 2006-05-31 2012-03-07 株式会社Ｉｈｉ Axial fluid device
FR2912790B1 (en) * 2007-02-16 2013-08-02 Snecma CIRCUIT ARRANGEMENT FOR AIR COLLECTION, COMPRESSOR STAGE COMPRISING IT, COMPRESSOR COMPRISING THEM AND TURBOJET ENGINEER COMPRISING THE SAME
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US7937929B2 (en) * 2007-11-16 2011-05-10 Pratt & Whitney Canada Corp. Exhaust duct with bypass channel
US8092145B2 (en) * 2008-10-28 2012-01-10 Pratt & Whitney Canada Corp. Particle separator and separating method for gas turbine engine
CN101871459B (en) * 2009-04-24 2013-10-30 德昌电机(深圳)有限公司 Discharge pump
US8668446B2 (en) 2010-08-31 2014-03-11 General Electric Company Supersonic compressor rotor and method of assembling same
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US9022730B2 (en) 2010-10-08 2015-05-05 General Electric Company Supersonic compressor startup support system
US8864454B2 (en) 2010-10-28 2014-10-21 General Electric Company System and method of assembling a supersonic compressor system including a supersonic compressor rotor and a compressor assembly
DE102010063071A1 (en) * 2010-12-14 2012-06-14 Rolls-Royce Deutschland Ltd & Co Kg Cooling device for a jet engine
US8657571B2 (en) 2010-12-21 2014-02-25 General Electric Company Supersonic compressor rotor and methods for assembling same
US8827640B2 (en) 2011-03-01 2014-09-09 General Electric Company System and methods of assembling a supersonic compressor rotor including a radial flow channel
US8550770B2 (en) 2011-05-27 2013-10-08 General Electric Company Supersonic compressor startup support system
US8770929B2 (en) 2011-05-27 2014-07-08 General Electric Company Supersonic compressor rotor and method of compressing a fluid
US9394792B2 (en) * 2012-10-01 2016-07-19 United Technologies Corporation Reduced height ligaments to minimize non-integral vibrations in rotor blades
US9810157B2 (en) 2013-03-04 2017-11-07 Pratt & Whitney Canada Corp. Compressor shroud reverse bleed holes
US9726084B2 (en) 2013-03-14 2017-08-08 Pratt & Whitney Canada Corp. Compressor bleed self-recirculating system
US20180313364A1 (en) * 2017-04-27 2018-11-01 General Electric Company Compressor apparatus with bleed slot including turning vanes
US10934943B2 (en) 2017-04-27 2021-03-02 General Electric Company Compressor apparatus with bleed slot and supplemental flange
US10808572B2 (en) * 2018-04-02 2020-10-20 General Electric Company Cooling structure for a turbomachinery component
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
US11725530B1 (en) * 2022-05-20 2023-08-15 General Electric Company Offtake scoops for bleed pressure recovery in gas turbine engines

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades

Also Published As

Publication number Publication date
WO1999051866A3 (en) 2001-07-19
DE69936939D1 (en) 2007-10-04
JP2003517525A (en) 2003-05-27
AU5201699A (en) 1999-10-25
DE69936939T2 (en) 2008-05-15
EP1147291B1 (en) 2007-08-22
EP1147291A4 (en) 2003-03-26
EP1147291A2 (en) 2001-10-24
ATE371097T1 (en) 2007-09-15
US6428271B1 (en) 2002-08-06
CA2321640C (en) 2004-01-06
WO1999051866A2 (en) 1999-10-14

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